US20170167391A1 - Fuel Control System For A Gas Turbine Engine Of An Aircraft - Google Patents

Fuel Control System For A Gas Turbine Engine Of An Aircraft Download PDF

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Publication number
US20170167391A1
US20170167391A1 US15/372,645 US201615372645A US2017167391A1 US 20170167391 A1 US20170167391 A1 US 20170167391A1 US 201615372645 A US201615372645 A US 201615372645A US 2017167391 A1 US2017167391 A1 US 2017167391A1
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United States
Prior art keywords
fuel
pump
pressure
control system
controller
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US15/372,645
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English (en)
Inventor
Salvatore Demelas
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Airbus Operations SL
Original Assignee
Airbus Operations SL
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Filing date
Publication date
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Publication of US20170167391A1 publication Critical patent/US20170167391A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/30—Control of fuel supply characterised by variable fuel pump output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/50—Application for auxiliary power units (APU's)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3013—Outlet pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/306—Mass flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a fuel control, pressurization and dispensing system for a gas turbine engine of an aircraft, in particular, for those aircrafts whose auxiliary power unit and/or main engine fuel control systems comprise a mechanical fuel control unit (FCU), a fuel controller (such as an Engine Electronic Unit (ECU)), and a plurality of nozzles for dispensing the pressurized fuel received from the FCU into the engine combustion chamber.
  • FCU mechanical fuel control unit
  • ECU Engine Electronic Unit
  • An aspect of the invention may provide a fuel control system that improves the performance and emission of conventional gas turbine engines, by decoupling the efficiency of the fuel pressurization and delivery into the combustion chamber from the operating phase (start, cooldown, idle, working, . . . ) and load condition (step load, full load, partial load, . . . ).
  • Another aspect of the present invention may provide a fuel control system that minimizes the weight of conventional fuel control systems, at the same time that simplifies the system, and avoids using the mechanical fuel control unit, allowing saving costs and space when installed in the aircraft.
  • the APU fuel control system is mainly a mechanical system where the fuel controller controls the engine by modulating the fuel pressure delivered to the nozzles from the fuel control unit.
  • a conventional fuel control system comprises a fuel tank ( 3 ) containing fuel, a FCU ( 4 ), an APU DC fuel pump ( 8 ) for feeding the FCU ( 4 ) from the fuel tank ( 3 ) when main engine fuel pumps are off, an APU gearbox ( 2 ) tor mechanically drive the FCU ( 4 ), at least one nozzle ( 10 ) for dispensing the pressurize fuel received from the FCU ( 4 ) into the APU combustion chamber ( 6 ), and said APU combustion chamber ( 6 ).
  • conventional systems comprise a fuel controller ( 5 ) adapted to modulate the fuel pressure delivered to the nozzles ( 10 ) by actuating on the FCU ( 4 ).
  • FIGS. 2 a - c show a conventional nozzle ( 10 ) dispensing fuel at different pressures.
  • the nozzle ( 10 ) is supplied with a low pressure of fuel.
  • the nozzle ( 10 ) is supplied with a medium pressure of fuel.
  • the nozzle ( 10 ) is supplied with a high pressure of fuel.
  • the atomization pattern is extended covering great areas and dispensing droplets of minimum size.
  • the present invention overcomes the above mentioned drawbacks by providing a fuel control system that improves the performance and emission of a gas turbine engine, at the same time that provides a simplified system with respect to conventional systems, and achieves a weight and cost reduction.
  • the invention refers to a fuel control system for a gas turbine engine of an aircraft that comprises an engine having a gearbox and a combustion chamber, and a fuel tank for containing fuel.
  • the system further comprises a high pressure fuel pump to pump fuel from the fuel tank towards the combustion chamber, at least one electrically controlled fuel injector to inject a flow rate of the pumped fuel into the combustion chamber, a fuel pressure sensor placed to sense the pressure of the pumped fuel, a fuel temperature sensor placed to sense the temperature of the pumped fuel, and a fuel controller electrically coupled with the fuel pressure and temperature sensors to calculate the fuel density according to the sensed values.
  • the fuel controller is electrically coupled with the at least one fuel injector to determine the fuel flow injection rate.
  • the fuel controller is adapted to calculate the quantity of the injected fuel, according to the fuel density and the fuel flow injection rate. Further, the fuel controller is electrically coupled with the fuel pump to establish a pump output pressure value, according to the quantity of the injected fuel, such that a constant fuel pressure value is supplied to the at least one fuel injector, in order to inject a constant fuel injection pressure in the combustion chamber.
  • the fuel controller is coupled with both the fuel pressure sensor and the fuel temperature sensor to calculate the pumped fuel density, and with the at least one fuel injector to measure the rate of injection that is being delivered by said injector. Based on the fuel density and on the flow injection rate, the fuel controller is capable of calculating the quantity of fuel that is being directly injected in the combustion chamber. According to this, the fuel controller is further adapted to establish an output pressure value on the fuel pump, such that a constant fuel pressure value is supplied to the at least one fuel injector. Thus, a constant fuel injection pressure is injected into the combustion chamber. This way, the required fuel injection rate is reliably injected at any time in the combustion chamber by the at least one fuel injector.
  • the FCU is a highly complex and heavy mechanical element that is mechanically driven by the gearbox, the describes system has a weight and simplicity improvement, and also a better response of the engine at any speed or load condition. Additionally, the fuel atomization is decoupled from the engine operation.
  • the DC powered fuel pump which conventionally feeds the FCU from the fuel tanks when the fuel pumps of the main engines are off, may be removed.
  • the fuel control system is simplified, and installation, recurrent, and direct costs of the mentioned components, and also of those other components required for their functioning, may be reduced. Thus, the maintenance costs involved by conventional systems are also reduced.
  • FIG. 1 shows a schematic view of a conventional fuel control system for an auxiliary power unit of an aircraft, in which a FCU, an APU DC powered fuel pump, and at least one nozzle is used for dispensing fuel from the fuel tank into the APU combustion chamber.
  • FIG. 3 shows a schematic view of a fuel control system according to an embodiment of the present invention.
  • FIG. 4 shows a schematic view of a fuel control system according to another embodiment of the present invention.
  • FIG. 6 shows a droplet pattern of a high pressure injection by the at least one electrically controlled fuel injector.
  • FIG. 3 shows a schematic view of a fuel control system 1 for a gas turbine engine of an aircraft according to an embodiment of the invention.
  • the fuel control system 1 of FIG. 3 comprises an engine 18 having a gearbox 2 and a combustion chamber 6 , and a fuel tank 3 for containing fuel.
  • the system 1 further comprises a high pressure fuel pump 9 , at least one electrically controlled fuel injector 7 , a fuel pressure sensor 11 , a fuel temperature sensor 12 , and a fuel controller 5 .
  • the high pressure fuel pump 9 is connected to the fuel tank 3 for pumping fuel from the tank 3 towards the combustion chamber 6 .
  • the fuel controller 5 is adapted to calculate the quantity of injected fuel to establish a pump output pressure value such that a constant fuel pressure value is supplied to the at least one fuel injector 7 .
  • a constant fuel injection pressure is injected in the combustion chamber 6 by the at least one fuel injector 7 .
  • the fuel control system 1 achieves supplying a high constant fuel pressure to the at least one fuel injector 7 , and thereby, dispensing a constant high fuel injection pressure into the combustion chamber 6 .
  • the fuel controller 5 is further adapted to regulate the fuel flow injection rate of the at least one fuel injector 7 for supplying the at least one fuel injector 7 with a high constant fuel pressure value. By regulating the fuel flow injection rate, the fuel controller 5 regulates the quantity of injected fuel.
  • the fuel controller 5 is adapted to control both the output pressure of the pumped fuel 9 , and the fuel flow of the at least one fuel injector 7 , for supplying the at least one fuel injector 7 with a high constant fuel pressure value.
  • the fuel flow rate of the fuel injector 7 can be varied by the fuel controller 5 for obtaining the desired instantaneous fuel quantity while ensuring a constant input pressure value with which supplying the at least one fuel injector 7 .
  • the engine 18 further comprises a shaft and the fuel control system 1 further comprises an engine speed sensor 14 , wherein the engine speed sensor 14 is coupled to the engine 18 to sense the instantaneous shaft speed value , and wherein the fuel controller 5 is further adapted to receive instantaneous engine load information 13 and to modify the fuel pump output pressure value considering load and speed values for supplying a constant fuel pressure value to the at least one fuel injector 7 .
  • the engine load information 13 can be estimated based on the fuel needed to keep the required engine speed at a given electrical and pneumatic load. This engine load information 13 can be provided by external signals, such as the air flow demand for the engine, or the thrust demand for the main engines.
  • the fuel controller 5 is adapted to modify both the output pressure of the fuel pump 9 and the fuel flow rate of the at least one fuel injector 7 , considering the load and speed values of the gas turbine engine in addition to the density and the flow injection rate of the pumped fuel.
  • the fuel controller 5 is further adapted to modify the duty cycle of the fuel pump 9 according to the load and speed values for that a constant fuel pressure value is supplied to the at least one fuel injector 7 .
  • the invention allows reducing the power consumption of the fuel pump, passing from a fuel pump in continuous maximum pressure operation, to a fuel pump with lower pressure operation.
  • the fuel pump 9 comprises input valves for receiving fuel to be pumped, and the fuel controller 5 is further adapted to reduce the pump input fuel flow through at least one of said fuel pump input valves, according to the load and/or speed values. This way, the high pressure pump power consumption is optimized.
  • the fuel control system 1 further comprises an input airflow pressure 15 and air temperature sensor 16 , both located in an engine air inlet, to respectively sense pressure and temperature values of the input airflow, and wherein the fuel controller 5 is further adapted to modify the fuel pump output pressure value considering the inlet airflow pressure and/or temperature values, for supplying a constant fuel pressure value to the at least one fuel injector 7 .
  • the fuel controller 5 is adapted to modify both the output pressure of the fuel pump 9 and the fuel flow rate of the at least one fuel injector 7 , considering the monitored engine air inlet pressure and temperature values to optimize the fuel injection flow rate taking into account the computed air density in addition to the load and speed values.
  • the fuel pressure sensor 11 and the fuel temperature sensor 12 are coupled to a pipeline 17 that connects the fuel pump 9 with the at least one fuel injector 7 .
  • the fuel pressure sensor 11 and the fuel temperature sensor 12 are coupled to an output of the fuel pump 9 .
  • the fuel pump 9 is a mechanical pump, which is mechanically driven by the gearbox 2 .
  • the fuel pump 9 is an electrical pump.
  • the fuel pump 9 can be decoupled from the gearbox 2 and can be located close to the fuel tanks.
  • the electrically powered fuel pump allows better control of the delivered fuel pressure, since it has no relation with the engine speed. Also, the electrical pump helps to save energy in case of low fuel demand.
  • the fuel control system 1 further comprises a linear motor, and the fuel pump 9 is driven by said linear motor.
  • a linear motor has a single friction point, involving fewer losses, less acoustic noise, and greater reliability.
  • the at least one fuel pump 9 is integrated into each injector 7 of the at least one fuel injector 7 to form a pump-injector element.
  • the pumping element can also be driven by a linear motor.
  • the gas turbine engine consists of an auxiliary power unit.
  • an aircraft comprises the fuel control system 1 as described.
  • the fuel control system presents the following advantages:
  • the current FCU is removed providing weight and system reliability improvements.
  • the fuel recirculation can be greatly reduced (if needed by the architecture of a specific fuel pressure powered engine actuator, or totally eliminated (return fuel manifolds can be removed). Fuel pump load can be optimized in line with the instantaneous engine need.
  • the engine fuel pressure powered actuators are not subject to fuel pressure variation which can alter their mechanical reaction time (which reduces the control loop fidelity and increases the engines SW regulation algorithm complexity).
  • High injection pressures increase the turbulence energy of the spray, which reduces the need of swirl energy losses in the combustor in order to produce the correct air-fuel mixture, which provides higher engine efficiency.
  • FIG. 6 shows a typical droplet pattern of a high pressure injection by the at least one electrically controlled fuel injector.
  • the droplet size of the fuel injectors of FIG. 6 is almost an order of magnitude lower than the size obtainable with the traditional nozzles of FIG. 5 .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
US15/372,645 2015-12-11 2016-12-08 Fuel Control System For A Gas Turbine Engine Of An Aircraft Abandoned US20170167391A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15382618.5A EP3179077B1 (de) 2015-12-11 2015-12-11 Kraftstoffregelsystem für gasturbinenmotor eines flugzeugs
EP15382618.5 2015-12-11

Publications (1)

Publication Number Publication Date
US20170167391A1 true US20170167391A1 (en) 2017-06-15

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US15/372,645 Abandoned US20170167391A1 (en) 2015-12-11 2016-12-08 Fuel Control System For A Gas Turbine Engine Of An Aircraft

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US (1) US20170167391A1 (de)
EP (1) EP3179077B1 (de)
ES (1) ES2698380T3 (de)

Cited By (13)

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CN111483601A (zh) * 2019-01-29 2020-08-04 波音公司 具有速度补偿的飞行器辅助动力单元（apu）控制系统
CN114051555A (zh) * 2019-07-03 2022-02-15 赛峰飞机发动机公司 确定用于在飞行器发动机的燃料供给回路中计量燃料的燃料密度的方法
CN114599867A (zh) * 2019-10-30 2022-06-07 通用电气公司 用于操作具有多种液体燃料的燃烧器的系统和方法
US20220212547A1 (en) * 2019-04-12 2022-07-07 Safran Helicopter Engines Hybrid propulsion installation and method for controlling such an installation
CN115492687A (zh) * 2021-06-17 2022-12-20 通用电气公司 管理热燃料的控制方法
US20220403785A1 (en) * 2019-08-30 2022-12-22 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine engine
US20220403783A1 (en) * 2021-06-17 2022-12-22 General Electric Company Methods of control for management of hot fuel
US11629717B2 (en) 2019-11-08 2023-04-18 Hamilton Sundstrand Corporation Simultaneously pumping and measuring density of aircraft fuel
US11635031B2 (en) * 2019-11-08 2023-04-25 Hamilton Sundstrand Corporation Simultaneously pumping and measuring density of aircraft fuel
US20230243305A1 (en) * 2022-02-02 2023-08-03 Rolls-Royce Plc Combination of a gas turbine engine and a power electronics
US11821366B2 (en) 2021-06-17 2023-11-21 General Electric Company Methods of control for management of hot fuel
US12031492B2 (en) 2021-10-12 2024-07-09 Hamilton Sundstrand Corporation Electric fuel control closed loop aircraft fuel system
US12392288B2 (en) 2022-02-02 2025-08-19 Rolls-Royce Plc Combination of a gas turbine engine and a power electronics

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US10988266B2 (en) 2019-01-29 2021-04-27 The Boeing Company Aircraft auxiliary power unit (APU) control system having speed compensation
US11034463B2 (en) 2019-03-26 2021-06-15 The Boeing Company Aircraft auxiliary power unit (APU) control system having variably sized air inlet
RU2753207C1 (ru) * 2020-10-14 2021-08-12 Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" Система подачи топлива в многоколлекторную камеру сгорания
CN114718737B (zh) * 2022-04-11 2023-09-05 中国航发控制系统研究所 一种电动燃油泵的流量开环控制方法

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2730167A (en) * 1950-03-08 1956-01-10 Chrysler Corp Control apparatus
US3157221A (en) * 1961-08-07 1964-11-17 Holley Carburetor Co Fluid supply system
US4508127A (en) * 1983-03-30 1985-04-02 The Garrett Corporation Fuel mass flow measurement and control system
US4747262A (en) * 1985-10-04 1988-05-31 Allied-Signal, Inc. Compressor power unit fuel flow control
US5351893A (en) * 1993-05-26 1994-10-04 Young Niels O Electromagnetic fuel injector linear motor and pump
US5515280A (en) * 1992-01-22 1996-05-07 Mitsubishi Denki Kabushiki Kaisha Electronic control device for a multi-fuel internal combustion engine
US20110041510A1 (en) * 2009-08-24 2011-02-24 Honda Motor Co., Ltd. Fuel control apparatus for gas turbine engine
US8126631B2 (en) * 2005-12-22 2012-02-28 Econox Technologies, Llc Apparatus and method for fuel flow rate, fuel temperature, fuel droplet size, and burner firing rate modulation
US20120271527A1 (en) * 2011-04-20 2012-10-25 Hamilton Sundstrand Corporation Distributed aircraft engine fuel system
US20140294559A1 (en) * 2013-03-28 2014-10-02 Solar Turbines Incorporated Multiple mode gas turbine engine gas fuel system with integrated control
US20160138583A1 (en) * 2014-11-06 2016-05-19 Caterpillar Inc. Variable Retraction Rate Pump and Method for Operating Same
US20160327274A1 (en) * 2013-12-19 2016-11-10 United Technologies Corporation Self-pumping fuel injector for a gas turbine engine and method of operation
US9752530B2 (en) * 2014-12-15 2017-09-05 Ford Global Technologies, Llc Methods and systems for fixed and variable pressure fuel injection

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5274996A (en) * 1991-10-11 1994-01-04 Allied-Signal, Inc. Closed loop fuel control system
US20120324905A1 (en) * 2011-06-27 2012-12-27 Behzad Hagshenas Apu fuel system and method

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2730167A (en) * 1950-03-08 1956-01-10 Chrysler Corp Control apparatus
US3157221A (en) * 1961-08-07 1964-11-17 Holley Carburetor Co Fluid supply system
US4508127A (en) * 1983-03-30 1985-04-02 The Garrett Corporation Fuel mass flow measurement and control system
US4747262A (en) * 1985-10-04 1988-05-31 Allied-Signal, Inc. Compressor power unit fuel flow control
US5515280A (en) * 1992-01-22 1996-05-07 Mitsubishi Denki Kabushiki Kaisha Electronic control device for a multi-fuel internal combustion engine
US5351893A (en) * 1993-05-26 1994-10-04 Young Niels O Electromagnetic fuel injector linear motor and pump
US8126631B2 (en) * 2005-12-22 2012-02-28 Econox Technologies, Llc Apparatus and method for fuel flow rate, fuel temperature, fuel droplet size, and burner firing rate modulation
US20110041510A1 (en) * 2009-08-24 2011-02-24 Honda Motor Co., Ltd. Fuel control apparatus for gas turbine engine
US20120271527A1 (en) * 2011-04-20 2012-10-25 Hamilton Sundstrand Corporation Distributed aircraft engine fuel system
US20140294559A1 (en) * 2013-03-28 2014-10-02 Solar Turbines Incorporated Multiple mode gas turbine engine gas fuel system with integrated control
US20160327274A1 (en) * 2013-12-19 2016-11-10 United Technologies Corporation Self-pumping fuel injector for a gas turbine engine and method of operation
US20160138583A1 (en) * 2014-11-06 2016-05-19 Caterpillar Inc. Variable Retraction Rate Pump and Method for Operating Same
US9752530B2 (en) * 2014-12-15 2017-09-05 Ford Global Technologies, Llc Methods and systems for fixed and variable pressure fuel injection

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Hydraulics & Pneumatics, "Engineering Essentials: Fundamentals of Hydraulic Pumps", January 2012, retrieved on 23 January 2018 at http://www.hydraulicspneumatics.com/200/TechZone/HydraulicPumpsM/Article/False/6401/TechZone-HydraulicPumpsM, pp.2-3. *

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US20220212547A1 (en) * 2019-04-12 2022-07-07 Safran Helicopter Engines Hybrid propulsion installation and method for controlling such an installation
US12508917B2 (en) * 2019-04-12 2025-12-30 Safran Helicopter Engines Hybrid propulsion installation and method for controlling such an installation
CN114051555A (zh) * 2019-07-03 2022-02-15 赛峰飞机发动机公司 确定用于在飞行器发动机的燃料供给回路中计量燃料的燃料密度的方法
US20220403785A1 (en) * 2019-08-30 2022-12-22 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine engine
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US20220389876A1 (en) * 2019-10-30 2022-12-08 General Electric Company System and method for operating a combustor with multiple liquid fuels
US12385444B2 (en) * 2019-10-30 2025-08-12 Ge Infrastructure Technology Llc System and method for operating a combustor with multiple liquid fuels
US11629717B2 (en) 2019-11-08 2023-04-18 Hamilton Sundstrand Corporation Simultaneously pumping and measuring density of aircraft fuel
US11635031B2 (en) * 2019-11-08 2023-04-25 Hamilton Sundstrand Corporation Simultaneously pumping and measuring density of aircraft fuel
US11668241B2 (en) * 2021-06-17 2023-06-06 General Electric Company Methods of control for management of hot fuel
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US20220403783A1 (en) * 2021-06-17 2022-12-22 General Electric Company Methods of control for management of hot fuel
US12460578B2 (en) 2021-06-17 2025-11-04 General Electric Company Methods of control for management of hot fuel
CN115492687A (zh) * 2021-06-17 2022-12-20 通用电气公司 管理热燃料的控制方法
US12031492B2 (en) 2021-10-12 2024-07-09 Hamilton Sundstrand Corporation Electric fuel control closed loop aircraft fuel system
US20230243305A1 (en) * 2022-02-02 2023-08-03 Rolls-Royce Plc Combination of a gas turbine engine and a power electronics
US11946417B2 (en) * 2022-02-02 2024-04-02 Rolls-Royce Plc Combination of a gas turbine engine and a power electronics
US12392288B2 (en) 2022-02-02 2025-08-19 Rolls-Royce Plc Combination of a gas turbine engine and a power electronics

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